The General Interpolants Method (GIM) code which solves the multidimensional Navier-Stokes equations for arbitrary geometric domains is described. The geometry module in the GIM code generates two and three dimensional grids over specified flow regimes, establishes boundary condition information and computes finite difference analogs for use in the GIM code numerical solution module. The technique can be classified as an algebraic equation approach. The geometry package uses multivariate...

Topics: NASA Technical Reports Server (NTRS), BOUNDARY VALUE PROBLEMS, FINITE DIFFERENCE THEORY, FLOW...

The source listing of a computer code for calculating the flow fields in a supersonic free stream is given. The application of this code to an inlet on an airbreathing missile is also presented.

Topics: NASA Technical Reports Server (NTRS), FLOW DISTRIBUTION, INLET FLOW, NUMERICAL FLOW VISUALIZATION,...

To support development of the Boeing-Rocketdyne RS84 rocket engine, a full-flow, reaction turbine geometry was integrated into the NASA-MSFC turbine air-flow test facility. A mechanical design was generated which minimized the amount of new hardware while incorporating all test and instrumentation requirements. This paper provides details of the mechanical design for this Turbine Air-Flow Task (TAFT) test rig. The mechanical design process utilized for this task included the following basic...

Topics: NASA Technical Reports Server (NTRS), DESIGN ANALYSIS, PERFORMANCE TESTS, FABRICATION, ROCKET...

The present investigation reports a study of bubble generation under reduced gravity conditions, using both a co-flow and a cross-flow configuration. This study may be used in the conceptual design of a space-based thermal management system. Ensuing two-phase flow void fraction can be accurately monitored using a single nozzle gas injection system within a continuous liquid flow conduit, as utilized in the present investigation. Accurate monitoring of void fraction leads to precise control of...

Topics: NASA Technical Reports Server (NTRS), BUBBLES, CONTINUUM FLOW, CROSS FLOW, FLOW GEOMETRY,...

A three dimensional, viscous computer code was used to calculate the mixing downstream of a typical turbofan mixer geometry. Experimental data obtained using pressure and temperature rakes at the lobe and nozzle exit stations were used to validate the computer results. The relative importance of turbulence in the mixing phenomenon as compared with the streamwise vorticity set up by the secondary flows was determined. The observations suggest that the generation of streamwise vorticity plays a...

Topics: NASA Technical Reports Server (NTRS), FLOW GEOMETRY, NOZZLE FLOW, THREE DIMENSIONAL FLOW, TURBOFAN...

Flow fields in supersonic inlet configurations were computed using the eliptic GIM code on the STAR computer. Spillage flow under the lower cowl was calculated to be 33% of the incoming stream. The shock/boundary layer interaction on the upper propulsive surface was computed including separation. All shocks produced by the flow system were captured. Linearized block implicit (LBI) schemes were examined to determine their application to the GIM code. Pure explicit methods have stability...

Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, COMPUTER PROGRAMS, HYPERBOLIC...

Choked flow rate and pressure profile data were taken and studied for a configuration consisting of four axially aligned, sequential Borda tubes of 1.9 length diameter ratio with separation distances of 0.8 and 30 tube diameters. For either case the flow rate data could be represented by a flow coefficient reduced temperature plot. At a separation distance of 30 tube diameters the pressure profiles dropped sharply at the entrance and recovered within each Borda tube; except at low temperatures,...

Topics: NASA Technical Reports Server (NTRS), BOUNDARY LAYER SEPARATION, FLOW VISUALIZATION, INLET...

The work to be presented herein was motivated largely by a desire to improve the understanding of oscillatory fluid mechanics inside a Stirling engine. To this end, a CFD project was undertaken at Cleveland State University with the goal of accurately predicting the fluid dynamics within an engine or engine component. Along with the CFD efforts, a code validation project was undertaken at the University of Minnesota. The material covered herein consists of four main parts. In section 1, an...

Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, ENGINE DESIGN, FLOW...

The unsteady cross flow analogy reduces the steady three dimensional separation flow problem into an unsteady two dimensional flow problem in which the section shape changes with time. The two dimensional VORSEP code is extended to the case of arbitrary body growth rates in order to generate the initial vortex structures for the three dimensional free vortex sheet (FVS) code. Automatic procedures to reduce the wing geometry definition to a set of cross flow plane sections corresponding to the...

Topics: NASA Technical Reports Server (NTRS), CROSS FLOW, LEADING EDGES, SEPARATED FLOW, TWO DIMENSIONAL...

It is shown that the shock wave intensity can be decreased by using modified trailing edge configurations to reduce or even completely compensate for the effect of the finite thickness of the trailing edge. A theoretical analysis is presented together with numerical results for two supersonic streams flowing off the trailing edge at different velocities. The analysis is based on an ideal gas model.

Topics: NASA Technical Reports Server (NTRS), FLOW GEOMETRY, SHOCK WAVE PROPAGATION, TRAILING EDGES,...

A wing-design study was conducted on a 65 degree swept leading-edge delta wing in which the wing geometry was modified to take advantage of the naturally occurring flow that forms over a slender wing in a supersonic flow field. Three-dimensional nonlinear analysis methods were used in the study which was divided into three parts: preliminary design, initial design, and final design. In the preliminary design, the wing planform, the design conditions, and the near-conical wing-design concept...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AIRCRAFT CONFIGURATIONS,...

The problem of buoyant-thermocapillary convection in cavities is governed by a relatively large number of nondimensional parameters, and there is consequently a large number of different types of flow that can be found in this system. Previous results give disjoint glimpses of a wide variety of qualitatively and quantitatively different results in widely different parts of parameter space. In this study, we report experiments on the primary and secondary instabilities in a geometry with equal...

Topics: NASA Technical Reports Server (NTRS), CONVECTIVE FLOW, CAPILLARY FLOW, BUOYANCY, ASPECT RATIO,...

Certain empirical rotor wake and turbulence relationships were developed using existing low speed rotor wave data. A tip vortex model was developed by replacing the annulus wall with a row of image vortices. An axisymmetric turbulence spectrum model, developed in the context of rotor inflow turbulence, was adapted to predicting the turbulence spectrum of the stator gust upwash.

Topics: NASA Technical Reports Server (NTRS), ROTOR BLADES (TURBOMACHINERY), ROTOR SPEED, STATOR BLADES,...

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Jul 5, 2010
07/10

by
Crowl, R. J.; Dunbar, W. R.; Wentworth, C. B

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Topics: COMBUSTION STABILITY, GAS JETS, HYDROGEN, RAMJET ENGINES, SPRAY NOZZLES, TURBINE ENGINES, FLOW...

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Jul 11, 2010
07/10

by
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Topics: DELTA WINGS, VORTEX SHEETS, FLOW GEOMETRY, STEADY FLOW, THREE DIMENSIONAL FLOW, UNSTEADY FLOW,...

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May 23, 2011
05/11

by
McCay, T. D.; McCay, M. H

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The objective of the Casting and Solidification Technology (CAST) experiment was to perform a detailed characterization of the effects of convection on the governing growth parameters for unidirectional dendritic solidification. It accomplished this by (1) Developing a unified model of dendritic growth during controlled solidification, (2) Measuring minimally disturbed (micro-g) solutal and thermal fields for verification of the model components, and (3) Conducting convection affected (one-g)...

Topics: THERMAL FATIGUE, THERMAL STRESSES, CRACKING (FRACTURING), DUCTED FLOW, RING STRUCTURES, LIQUID...

A coupled strongly implicit method is combined with a deferred-corrector spline solver for the vorticity-stream function form of the Navier-Stokes equation. Solutions for cavity, channel and cylinder flows are obtained with the fourth-order spline 4 procedure. The strongly coupled spline corrector method converges as rapidly as the finite difference calculations and also allows for arbitrary large time increments for the Reynolds numbers considered. In some cases fourth-order smoothing or...

Topics: NASA Technical Reports Server (NTRS), NAVIER-STOKES EQUATION, SPLINE FUNCTIONS, STREAM FUNCTIONS...

The preparation of geometric data for input to three-dimensional potential flow programs was automated and simplified by a geometry package incorporated into the NASA Langley version of the 3-D lifting potential flow program. Input to the computer program for the geometry package consists of a very sparse set of coordinate data, often with an order of magnitude of fewer points than required for the actual potential flow calculations. Isolated components, such as wings, fuselages, etc. are...

Topics: NASA Technical Reports Server (NTRS), COMPUTER PROGRAMMING, FLOW GEOMETRY, INPUT/OUTPUT ROUTINES,...

Experimental and empirical model results are presented that extend previous studies of the mixing of single-sided and opposed rows of jets in a confined duct flow to include effects of non-circular orifices and double rows of jets. Analysis of the mean temperature data obtained in this investigation showed that the effects of orifice shape and double rows are significant only in the region close to the injection plane, provided that the orifices are symmetric with respect to the main flow...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, GAS TURBINE ENGINES, JET FLOW, JET...

Mean velocity and turbulence measurements were conducted on the three dimensional fountain flow field generated by the impingement of two axisymmetric jets on a ground plane with application to vertical takeoff and landing (VTOL) aircraft. The basic instantaneous velocity data were obtained using a two component laser Doppler velocimeter in a plane connecting the nozzle centerlines at different heights above the ground emphasizing the jet impingement region and the fountain upwash region formed...

Topics: NASA Technical Reports Server (NTRS), FLOW GEOMETRY, JET IMPINGEMENT, LASER DOPPLER VELOCIMETERS,...

Results from a recently completed enhanced mixing program are summarized in the two technical papers. These studies were parts of a High Speed Research (HSR)-supported joint Government/industry/university program that involved, in addition to the NASA Lewis Research Center, researchers at United Technologies Research Center, Allison Engine Company, CFD Research Corporation, and the University of California, Irvine. The studies investigated the mixing of jets injected normal to a confined...

Topics: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, CROSS FLOW, FLOW GEOMETRY, GAS TURBINE...

The linear aeroelastic equations for one curved blade of a vertical axis wind turbine in state vector form are presented. The method is based on a simple integrating matrix scheme together with the transfer matrix idea. The method is proposed as a convenient way of solving the associated eigenvalue problem for general support conditions.

Topics: NASA Technical Reports Server (NTRS), AEROELASTICITY, AXIAL FLOW TURBINES, LINEAR EQUATIONS, ROTOR...

The atmospheric general circulation experiment (AGCE) numerical design for Spacelab flights was studied. A spherical baroclinic flow experiment which models the large scale circulations of the Earth's atmosphere was proposed. Gravity is simulated by a radial dielectric body force. The major objective of the AGCE is to study nonlinear baroclinic wave flows in spherical geometry. Numerical models must be developed which accurately predict the basic axisymmetric states and the stability of...

Topics: NASA Technical Reports Server (NTRS), ATMOSPHERIC CIRCULATION, ATMOSPHERIC PHYSICS, AXISYMMETRIC...

The unsteady phenomena in the wake of an oscillating wing or rotor blade are examined theoretically using the Prandtl approximation of the vortex-transport equation. A mathematical model is developed and applied to such problems as the effect of winglets on the performance of fixed wings and the possibly of employing similar designs in rotor blades. Model predictions for several profiles are compared with published and experimental measurements, and good agreement is found. Graphs and diagrams...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AEROELASTICITY, AIRFOILS, WAKES,...

No abstract available

Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, SHOCK WAVE INTERACTION, SHOCK...

The application of the elements of quantum (wave) mechanics to some special problems in the field of macroscopic fluid dynamics is discussed. Emphasis is placed on the flow of a viscous, incompressible fluid around a circular cylinder. The following subjects are considered: (1) the flow of a nonviscous fluid around a circular cylinder, (2) the restrictions imposed the stream function by the number of dimensions of space, and (3) the flow past three dimensional bodies in a viscous fluid,...

Topics: NASA Technical Reports Server (NTRS), BOUNDARY LAYER FLOW, CYLINDRICAL BODIES, FLOW GEOMETRY, FLUID...

Computational and experimental results are presented for a case study of single injectors employed in 90 deg transverse injection into a non-reacting subsonic flow. Different injector orifice shapes are used (including circular, square, diamond-shaped, and wide rectangular slot), all with constant cross-sectional area, to observe the effects of this variation on injector penetration and mixing. Whereas the circle, square, and diamond injector produce similar jet plumes, the wide rectangular...

Topics: NASA Technical Reports Server (NTRS), ORIFICES, SHAPES, TURBULENCE MODELS, COMPUTATIONAL FLUID...

A cell-vertex scheme for the Navier-Stokes equations, which is based on central difference approximations and Runge-Kutta time stepping, is described. Using local time stepping, implicit residual smoothing, a multigrid method, and carefully controlled artificial dissipative terms, very good convergence rates are obtained for a wide range of two- and three-dimensional flows over airfoils and wings. The accuracy of the code is examined by grid refinement studies and comparison with experimental...

Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, FLOW GEOMETRY, NAVIER-STOKES...

The objectives are to: (1) Understand the influence in low gravity of flow on interface shape. For example, document and control the influence of axial flow on the Plateau-Rayleigh instability of a liquid bridge; and (2) Extend the ground-based density-matching technique of low gravity simulation to situations with flow; that is, develop Plateau chamber experiments for which flow can be controlled. Containerless containment of liquid by surface tension has broad importance in low gravity. For...

Topics: NASA Technical Reports Server (NTRS), FLOW GEOMETRY, FLUID DYNAMICS, INTERFACE STABILITY,...

For abstract, see

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, ENGINE INLETS, INLET FLOW, NOISE...

Experiments were conducted in a model tunnel scaled down in a ratio of 1:24 from the full size prototype V/STOL tunnel at NASA Langley Research Center. The flow characteristics around the tunnel were studied and the location and causes of local flow separation and local recirculation were documented. The study of the interaction between the various components from which the tunnel is built, an experimental setup similar to the sequence of tunnel circuit components was constructed which enabled...

Topics: NASA Technical Reports Server (NTRS), FLOW DISTRIBUTION, LOW SPEED WIND TUNNELS, VELOCITY...

A numerical analysis methodology and solutions of the interaction between the power stream and multiply-connected multi-cavity sealed secondary flow fields are presented. Flow solutions for a multi-cavity experimental rig were computed and compared with experimental data of Daniels and Johnson. The flow solutions illustrate the complex coupling between the main-path and the cavity flows as well as outline the flow thread that exists throughout the subplatform multiple cavities and seals. The...

Topics: NASA Technical Reports Server (NTRS), CAVITY FLOW, COMPUTATIONAL FLUID DYNAMICS, FLOW DISTRIBUTION,...

The curved flow capability of a stability wind tunnel was used to investigate the lateral directional characteristics of an F-18 aircraft. The model is described and the procedures used to obtain and correct the data and a graphical presentation of the results are presented. The results include graphs of lateral directional derivatives versus sideslip or static plots, the lateral directional static stability derivatives versus angle of attack, and finally the lateral directional derivatives...

Topics: NASA Technical Reports Server (NTRS), AIRCRAFT STABILITY, F-18 AIRCRAFT, FLOW GEOMETRY, LATERAL...

Results of a program for sonic inlet technology development are presented. This program includes configuration and mechanical design selection of concepts, aerodynamic design description of the models, and results of test evaluation. Several sonic inlet concepts were tested and compared for aerodynamic and acoustic performance. Results of these comparative evaluations are presented. Near-field measurements were taken inside several of the inlet models. Results of these tests are discussed with...

Topics: NASA Technical Reports Server (NTRS), ACOUSTIC PROPERTIES, AERODYNAMIC CONFIGURATIONS, ENGINE...

The flow in a two-dimensional curved channel driven by an azimuthal pressure gradient can become linearly unstable due to axisymmetric perturbations and/or nonaxisymmetric perturbations depending on the curvature of the channel and the Reynolds number. For a particular small value of curvature, the critical neighborhood of this curvature value and critical Reynolds number, nonlinear interactions occur between these perturbations. The Stuart-Watson approach is used to derive two coupled Landau...

Topics: NASA Technical Reports Server (NTRS), CHANNEL FLOW, CURVATURE, FLOW GEOMETRY, NONLINEARITY,...

Recent extensions and applications of the methods are emphasized. They include the specification of the Kutta condition for a slotted inlet, the calculation of suction and tangential blowing for boundary layer control, and the analysis of auxiliary inlet geometries at angles of attack. A comparison is made with experiment for the slotted inlet. An optimum diffuser velocity distribution was developed.

Topics: NASA Technical Reports Server (NTRS), BOUNDARY LAYER SEPARATION, ENGINE INLETS, INLET FLOW, V/STOL...

As part of an effort to develop computational techniques for design of natural laminar flow fuselages, a computational study was made of the effect of forebody geometry on laminar boundary layer stability on axisymmetric body shapes. The effects of nose radius on the stability of the incompressible laminar boundary layer was computationally investigated using linear stability theory for body length Reynolds numbers representative of small and medium-sized airplanes. The steepness of the...

Topics: NASA Technical Reports Server (NTRS), BOUNDARY LAYER STABILITY, FLOW GEOMETRY, FOREBODIES, LAMINAR...

Analytical capabilities for modeling hot gas flow on the fuel side of the Space Shuttle Main Engines are developed. Emphasis is placed on construction and documentation of a computational grid code for modeling an elliptical two-duct version of the fuel side hot gas manifold. Computational results for flow past a support strut in an annular channel are also presented.

Topics: NASA Technical Reports Server (NTRS), DUCTED FLOW, FLOW DISTRIBUTION, FLOW GEOMETRY, SPACE SHUTTLE...

The results of three distinct efforts whose common goal was to enhance the applicability and utility of the EHPIC (Evaluation of Hover Performance using Influence Coefficients) free wake hover performance prediction program are summarized. The primary task in this three-part effort revolved around the addition of an image wake to the original version of the EHPIC analysis to permit exploration of the effect of ground proximity on rotor performance. Representative calculations were carried out...

Topics: NASA Technical Reports Server (NTRS), APPLICATIONS PROGRAMS (COMPUTERS), GROUND EFFECT...

This program of theoretical and experimental ground-based research focuses on the understanding of the dynamics and stability limits of nonaxisymmetric and symmetric liquid bridges. There are three basic objectives: First, to determine the stability limits of nonaxisymmetric liquid bridges held between non-coaxial parallel disks, Second, to examine the dynamics of nonaxisymmetric bridges and nonaxisymmetric oscillations of initially axisymmetric bridges. The third objective is to experimentally...

Topics: NASA Technical Reports Server (NTRS), FLOW GEOMETRY, FLUID DYNAMICS, LIQUID BRIDGES, MICROGRAVITY,...

Cooling Flow Reduction: a) Focus on improving turbine hot gas path part cooling efficiency. b) Applicable to current metallic turbine components and synergistic with advanced materials. c) Address challenges of IGCC/hydrogen fuel environment (for example, possible cooling hole plugging). Leakage Flow Reduction: a) Focus on decreasing turbine parasitic leakages, i.e. between static-to-static, static-to-rotating turbine parts. b) Develop improved seal designs in a variety of important areas....

Topics: NASA Technical Reports Server (NTRS), HEAT TRANSFER, TURBINES, HIGH TEMPERATURE GASES, GAS PATH...

An experimental investigation of turbine disk cavity aerodynamics and heat transfer was conducted to provide an experimental data base that can guide the aerodynamic and thermal design of turbine disks and blade attachments for flow conditions and geometries simulating those of the space shuttle main engine (SSME) turbopump drive turbines. Experiments were conducted to define the nature of the aerodynamics and heat transfer of the flow within the disk cavities and blade attachments of a large...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AERODYNAMIC HEAT TRANSFER,...

This is the final report of the NASA Lewis SBIR Phase 2 Contract Number NAS3-25785, Multigrid Solution of Internal Flows Using Unstructured Solution Adaptive Meshes. The objective of this project, as described in the Statement of Work, is to develop and deliver to NASA a general three-dimensional Navier-Stokes code using unstructured solution-adaptive meshes for accuracy and multigrid techniques for convergence acceleration. The code will primarily be applied, but not necessarily limited, to...

Topics: NASA Technical Reports Server (NTRS), BOUNDARY CONDITIONS, COMPUTATIONAL GRIDS, GRID GENERATION...

This paper is concerned with the prediction of the low cycle thermal fatigue behavior of a component in a developmental (ATD) high pressure liquid oxygen turbopump (HPOTP) for the Space Shuttle Main Engine (SSME). This component is called the Turnaround Duct (TAD). The TAD is a complex single piece casting of MAR-M-247 material. Its function is to turn the hot turbine exhaust gas (1200 F hydrogen rich gas steam) such that it can exhaust radially out of the turbopump. In very simple terms, the...

Topics: NASA Technical Reports Server (NTRS), THERMAL FATIGUE, TURBINE PUMPS, SPACE SHUTTLE MAIN ENGINE,...

A Galilean invariant weak-equilbrium hypothesis that is sensitive to streamline curvature is proposed. The hypothesis leads to an algebraic Reynolds stress model for curved flows that is fully explicit and self-consistent. The model is tested in curved homogeneous shear flow: the agreement is excellent with Reynolds stress closure model and adequate with available experimental data.

Topics: NASA Technical Reports Server (NTRS), TURBULENCE MODELS, MATHEMATICAL MODELS, REYNOLDS STRESS,...

Experimental measurements in the inlet of a transonic turbine blade cascade showed unacceptable pitchwise flow non-uniformity. A three-dimensional, Navier-Stokes computational fluid dynamics (CFD) analysis of the imbedded bellmouth inlet in the facility was performed to identify and eliminate the source of the flow non-uniformity. The blockage and acceleration effects of the blades were accounted for by specifying a periodic static pressure exit condition interpolated from a separate...

Topics: NASA Technical Reports Server (NTRS), THREE DIMENSIONAL FLOW, DIMENSIONAL ANALYSIS, NAVIER-STOKES...

Total-pressure-loss coefficients, flow discharge coefficients, and friction factors were determined experimentally for the various area and geometry changes and flow passages within an air-cooled turbine vane. The results are compared with those of others obtained on similar configurations, both actual and large models, of vane passages. The supply and exit air pressures were controlled and varied. The investigation was conducted with essentially ambient-temperature air and without external...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC COEFFICIENTS, AIR FLOW, PRESSURE DISTRIBUTION,...

Tests were conducted on a high-tip-speed, low-loading transonic fan stage to determine the performance and inlet flow distortion tolerance of the design. The fan was designed for high efficiency at a moderate pressure ratio by designing the hub section to operate at minimum loss when the tip operates with an oblique shock. The design objective was an efficiency of 86 percent at a pressure ratio of 1.5, a specific flow (flow per unit annulus area) of 42 lb/sec-sq. ft (205.1 kgm/sec-m sq), and a...

Topics: NASA Technical Reports Server (NTRS), AIR FLOW, FLOW GEOMETRY, PROPULSIVE EFFICIENCY, TRANSONIC...

An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance of seven inlets having NACA 1-series contours and one inlet having an elliptical contour over a range of mass-flow ratios and at angle of attack. The inlet diameter ratio varied from 0.81 to 0.89; inlet length ratio varied from 0.75 to 1.25; and internal contraction ratio varied from 1.009 to 1.093. Reynolds number based on inlet maximum diameter varied from 3.4 million at a Mach number of 0.4 to...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, AIR FLOW, ENGINE INLETS, FLOW...

The potential-flow velocity distributions on several splitter geometries in an engine inlet and their variation with different splitter leading-edge shapes and distances from the inlet highlight were analyzed. The velocity distributions on the inner and outer surfaces of the splitters are presented for low-speed and cruise conditions. At zero incidence angle, the splitter with the 4-to-1 elliptical leading edge had lower peak velocities and velocity gradients than the splitter with the 2-to-1...

Topics: NASA Technical Reports Server (NTRS), ENGINE INLETS, FLOW GEOMETRY, INLET FLOW, VELOCITY...